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Abstract

A three-dimensional inviscid flow solver is developed for, predicting the aerodynamic performance of hovering helicopter rotor blades using unstructured meshes. The flow solver utilizes a cell-centered finite-volume scheme that is based on the Roe`s flux-difference splitting with an implicit Jacobi/Gauss-Seidel time integration. Calculation is performed for a transonic tip Mach number operating condition. A solution-adaptive mesh is used to improve the accuracy of the solution not only on the blade surface but also in the wake. It is demonstrated that the tip vortex geometry can be accurately captured using the present mesh adaptation procedure. Good agreements are obtained between the numerical result and the experiment for both the blade loading and the tip vortex behavior.